STUDY OF BOUNDARY LAYER SEPARATION ON FUSELAGE DUE TO TAIL ENGINE

Manish Kumar, Abdul Rahman Ansari, Hassan Ansari, Ankush Dandale

Abstract: The main purpose of our project is to study the boundary layer separation over the fuselage and how it is affected due to introduction of tail engine. For the following purpose we considered a cylindrical pipe as fuselage and used propeller as the tail engine. We tested our model in the wind tunnel at different positions (10cm, 20cm, 30cm from rear edge of fuselage), different velocities of wind tunnel (6.2m/s, 9m/s, 12.4m/s) and different motor rpm (rpm=0, rpm=175, rpm=350) and concluded our results whether the boundary layer shifts or not by placing tail engine. If it shifts, at what position it will be most suitable to place the engine. We noted height in manometer and obtained pressure and normal reaction force. After that, we calculated drag and found without engine mounting, there will be more drag but after placing engine at the rear of the fuselage we concluded that the skin friction drag is reduced substantially. From above experimental result we concluded that, the drag is gradually decreasing as we are on increasing rpm of mounted motor but when air flow velocity is increases, some drag also increases due to shift of air flow from laminar to the turbulence.

Keywords: Boundary Layer, Fuselage, Rear Engine, Wind Turbine, Throttle

DOI: https://doi.org/10.15623/ijret.2017.0603004